Flow characteristics of leading edge erosion subsonic airfoil under low Reynolds number condition
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摘要:
以某涡扇发动机风扇叶片亚声叶型为研究对象，参考美国标准大气推广委员会（COESA）的大气模型，对原始叶型和两种前缘侵蚀叶型在5个大气高度下进行数值模拟计算，探究在高空低雷诺数环境下前缘侵蚀对亚声叶栅流动特性的影响。结果表明：0°攻角下低雷诺数条件削弱了气流在前缘处对前缘形貌的敏感程度，使得3种叶型前缘处压力分布、吸力面边界层的流动分离与转捩、尾缘分离程度均趋于一致，最终表现为由前缘侵蚀引起的总压损失增大量随着雷诺数降低而减小，3种叶型的总压损失系数和压比趋于一致。而在4°攻角下，前缘侵蚀在低雷诺数下可以促进转捩的发生，减小尾缘分离程度，进而使得总压损失小于0°攻角的情况，在进口马赫数为0.6时降低了23.6%，在进口马赫数为0.8时则降低了41.2%。
Abstract:Taking the subsonic airfoil of a turbofan engine fan blade as the research object, numerical simulation of the original airfoil and two leading edge erosion airfoils at five atmospheric heights was carried out with reference to the Committee on Extension to the Standard Atmosphere (COESA) standard atmospheric model, so as to explore the influence of leading edge erosion on the flow characteristics of subsonic cascade in high altitude and low Reynolds number environment. The results showed that at 0° angle of attack, the low Reynolds number condition weakened the sensitivity of the airflow to the leading edge morphology, so that the pressure distribution at the leading edge, the flow separation and transition of the boundary layer on the suction surface, and the separation degree of the trailing edge of the three airfoils tended to be consistent. Finally, the increase of total pressure loss caused by the leading edge erosion became smaller with the decrease of Reynolds number, and the total pressure loss coefficient and pressure ratio of the three airfoils tended to be consistent. At the angle of attack of 4°, the leading edge erosion can promote the occurrence of transition at low Reynolds number and reduce the degree of trailing edge separation, so that the total pressure loss was less than 0° angle of attack; when the inlet Mach number was 0.6, it reduced by 23.6%, and when 0.8, it reduced by 41.2%.
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Key words:
- low Reynolds number /
- subsonic cascade /
- leading edge erosion /
- boundary layer /
- flow separation /
- transition
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图 1 原始叶型和两种侵蚀叶型示意图
Figure 1. Schematic diagram of the original airfoil and two eroded airfoils
图 3 数值模拟结果和实验数据对比
Figure 3. Comparison of numerical simulation results with experimental data
图 5 3种叶型在不同雷诺数下的压比
Figure 5. Pressure ratios of three airfoils at different Reynolds numbers
图 6 3种叶型在不同雷诺数下的总压损失系数
Figure 6. Total pressure loss coefficients of three airfoils at different Reynolds numbers
图 7 ORG叶型在不同高度的表面静压系数曲线
Figure 7. Static pressure coefficients of ORG airfoils at different altitudes
图 8 3种叶型在不同雷诺数下的表面静压系数
Figure 8. Static pressure coefficients of three airfoils at different Reynolds numbers
图 9 3种叶型在不同雷诺数下的尾迹局部总压损失系数
Figure 9. Local total pressure loss coefficient of the wake of three airfoils at different Reynolds numbers
图 10 ORG叶型在不同高度的形状因子及间歇因子曲线
Figure 10. Shape factor and intermittency factor curves of the ORG profile at different altitudes
图 11 Main =0.6时ORG叶型吸力面马赫数云图
Figure 11. Mach number contours of suction side of ORG airfoil at Main =0.6
图 12 3种叶型在不同高度的形状因子及法向平均间歇因子
Figure 12. Shape factor and normal mean intermittency factor of the three airfoils at different altitudes
图 13 α=0°，4°攻角下3种叶型在不同雷诺数下的总压损失系数和压比对比
Figure 13. Comparison of total pressure loss coefficients and static pressure ratio of three airfoils at different Reynolds numbers at α=0°，4°
图 14 α=4°下3种叶型在不同高度的形状因子和法向平均间歇因子对比
Figure 14. Comparison of shape factor and intermittency factor of three airfoils at different altitudes at α=4°
图 15 Main=0.6，α=4°时3种叶型在不同高度下的前缘分离泡云图
Figure 15. Contours of leading edge separation bubble of three airfoils at different altitudes atMain=0.6，α=4°
图 16 h=15 km，Main =0.8，α=4°时ORG叶型前缘分离泡云图
Figure 16. Contour of leading edge separation bubbles of the ORG airfoil at h=15 km，Main =0.8，α=4°
表 1 原始叶型相关参数
Table 1. Parameters related to the original airfoil
参数 数值 进口马赫数 <0.9 弦长/mm 257.67 安装角/（°） 45.97 进口几何角/（°） 37.4 出口几何角/（°） 31.89 栅距/mm 132.66 
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表 2 5个高度层的大气数据
Table 2. Atmospheric data of 5 altitude layers
高度/
km大气模型参数 参考压力/Pa 温度/K 密度/（kg/m3） 声速/（m/s） 8 35600 236.15 0.5252 308.06 10 26436 223.15 0.4172 299.46 15 12045 216.65 0.1937 295.07 20 5475 216.65 0.088 295.07 25 2511 221.65 0.0395 298.46
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[1] 唐民锋. 军用无人机发动机维修保障特点及发展趋势[J]. 航空维修与工程, 2017(4): 38-40. TANG Minfeng. Support characteristics and development trend of military UAV engine[J]. Aviation Maintenance & Engineering, 2017(4): 38-40. (in Chinese doi: 10.3969/j.issn.1672-0989.2017.04.017TANG Minfeng. Support characteristics and development trend of military UAV engine[J]. Aviation Maintenance & Engineering, 2017(4): 38-40. (in Chinese) doi: 10.3969/j.issn.1672-0989.2017.04.017 [2] 于广民, 王奉明, 卢娟. 高空长航时无人机用发动机推力需求及技术特点分析[J]. 燃气涡轮试验与研究, 2021, 34(6): 41-46, 55. YU Guangmin, WANG Fengming, LU Juan. Analysis of engine requirements and technical characteristics for high altitude long endurance UAV[J]. Gas Turbine Experiment and Research, 2021, 34(6): 41-46, 55. (in Chinese doi: 10.3969/j.issn.1672-2620.2021.06.009YU Guangmin, WANG Fengming, LU Juan. Analysis of engine requirements and technical characteristics for high altitude long endurance UAV[J]. Gas Turbine Experiment and Research, 2021, 34(6): 41-46, 55. (in Chinese) doi: 10.3969/j.issn.1672-2620.2021.06.009 [3] 吴川, 赵军. 民用大涵道比涡扇发动机性能分析[J]. 科学技术与工程, 2022, 22(27): 12208-12216. WU Chuan, ZHAO Jun. Performance analysis of civil turbofan engine with large bypass-ratio[J]. Science Technology and Engineering, 2022, 22(27): 12208-12216. (in ChineseWU Chuan, ZHAO Jun. Performance analysis of civil turbofan engine with large bypass-ratio[J]. Science Technology and Engineering, 2022, 22(27): 12208-12216. (in Chinese) [4] 肖洪, 吴虎, 廉筱纯. 雷诺数对涡扇发动机性能及稳定性影响[J]. 航空动力学报, 2005, 20(3): 394-398. XIAO Hong, WU Hu, LIAN Xiaochun. Reynolds number effects on performance and aerodynamic stabilities of the turbofan engines[J]. Journal of Aerospace Power, 2005, 20(3): 394-398. (in Chinese doi: 10.3969/j.issn.1000-8055.2005.03.010XIAO Hong, WU Hu, LIAN Xiaochun. Reynolds number effects on performance and aerodynamic stabilities of the turbofan engines[J]. Journal of Aerospace Power, 2005, 20(3): 394-398. (in Chinese) doi: 10.3969/j.issn.1000-8055.2005.03.010 [5] 王进, 骆广琦, 陶增元. 雷诺数对压气机特性及发动机稳定性影响的计算和分析[J]. 航空动力学报, 2003, 18(1): 20-23. WANG Jin, LUO Guangqi, TAO Zengyuan. Effects of Reynolds number on compressor performance and engine stability[J]. Journal of Aerospace Power, 2003, 18(1): 20-23. (in ChineseWANG Jin, LUO Guangqi, TAO Zengyuan. Effects of Reynolds number on compressor performance and engine stability[J]. Journal of Aerospace Power, 2003, 18(1): 20-23. (in Chinese) [6] 梁俊, 赵正, 刘晓晨, 等. 雷诺数对高负荷轴流压气机性能及稳定性影响的试验研究[J]. 燃气涡轮试验与研究, 2023, 36(1): 16-22. LIANG Jun, ZHAO Zheng, LIU Xiaochen, et al. Experimental study of effects of Reynolds number on performance and stability of high load axial compressors[J]. Gas Turbine Experiment and Research, 2023, 36(1): 16-22. (in ChineseLIANG Jun, ZHAO Zheng, LIU Xiaochen, et al. Experimental study of effects of Reynolds number on performance and stability of high load axial compressors[J]. Gas Turbine Experiment and Research, 2023, 36(1): 16-22. (in Chinese) [7] 郭捷, 王咏梅, 杜辉, 等. 低雷诺数条件对涡扇发动机风扇/压气机性能和稳定性影响的试验研究[J]. 航空发动机, 2004, 30(4): 4-6. GUO Jie, WANG Yongmei, DU Hui, et al. Experimental investigation of low Reynolds number effects on fan/compressor performance and stability for turbofans[J]. Aeroengine, 2004, 30(4): 4-6. (in Chinese doi: 10.3969/j.issn.1672-3147.2004.04.002GUO Jie, WANG Yongmei, DU Hui, et al. Experimental investigation of low Reynolds number effects on fan/compressor performance and stability for turbofans[J]. Aeroengine, 2004, 30(4): 4-6. (in Chinese) doi: 10.3969/j.issn.1672-3147.2004.04.002 [8] 王奉明, 程卫华. 高空长航时无人机用涡扇发动机关键技术分析[J]. 燃气涡轮试验与研究, 2010, 23(4): 53-56, 34. WANG Fengming, CHENG Weihua. An analysis of key technologies for turbofan engine of HALE UAV[J]. Gas Turbine Experiment and Research, 2010, 23(4): 53-56, 34. (in Chinese doi: 10.3969/j.issn.1672-2620.2010.04.012WANG Fengming, CHENG Weihua. An analysis of key technologies for turbofan engine of HALE UAV[J]. Gas Turbine Experiment and Research, 2010, 23(4): 53-56, 34. (in Chinese) doi: 10.3969/j.issn.1672-2620.2010.04.012 [9] 任鹏, 李丽丽, 刘太秋. 高速涡轮发动机压缩部件低雷诺数影响研究[J]. 航空发动机, 2023, 49(1): 68-75. RENG Peng, LI Lili, LIU Taiqiu. Research on the influence of low Reynolds number on the compression component of high-speed turbine engine[J]. Aeroengine, 2023, 49(1): 68-75. (in ChineseRENG Peng, LI Lili, LIU Taiqiu. Research on the influence of low Reynolds number on the compression component of high-speed turbine engine[J]. Aeroengine, 2023, 49(1): 68-75. (in Chinese) [10] RHODEN H G. Effects of Reynolds number on the flow of air through cascades of compressor blades: R&M No. 2919[R]. London: Her Majesty’s Stationery Office, 1956. [11] STUART D J. Analysis of Reynolds number effects in fluid flow through two dimensional cascades: R&M No. 2920[R]. London: Her Majesty’s Stationery Office, 1955. [12] WASSELL A B. Reynolds number effects in axial compressors[J]. Journal of Engineering for Power, 1968, 90(2): 149-156. doi: 10.1115/1.3609154 [13] HEINZ A S, WOLFGANG S, BERNHARD K. Effects of Reynolds number and free-stream turbulence on boundary layer transition in a compressor cascade[J]. Journal of Turbomachinery, 200, 124(1): 1-9. [14] SONODA T, SCHREIBER H A. Aerodynamic characteristics of supercritical outlet guide vanes at low Reynolds number conditions[J]. Journal of Turbomachinery, 2007, 129(4): 694-704. doi: 10.1115/1.2720868 [15] ROEHLE I, LE GUEVEL A, FRADIN C. 3D-shock visualization in a transonic compressor rotor[J]. Optics & Laser Technology, 1999, 31(1): 67-73. [16] SONODA T, YAMAGUCHI Y, ARIMA T, et al. Advanced high turning compressor airfoils for low Reynolds number condition: Part 1 design and optimization[J]. Journal of Turbomachinery, 2004, 126(3): 350-359. doi: 10.1115/1.1737780 [17] SCHREIBER H A, STEINERT W, SONODA T, et al. Advanced high turning compressor airfoils for low Reynolds number condition: Part 2 experimental and numerical analysis[J]. Journal of Turbomachinery, 2004, 126(4): 482-492. doi: 10.1115/1.1737781 [18] DONG Hao, XIA Tianyu, CHEN Lin, et al. Study on flow separation and transition of the airfoil in low Reynolds number[J]. Physics of Fluids, 2019, 31(10): 103601. doi: 10.1063/1.5118736 [19] WANG Mingyang, LI Ziliang, ZHAO Shengfeng, et al. Effects of Reynolds number and loading distribution on the aerodynamic performance of a high subsonic compressor airfoil[J]. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 2020, 234(8): 1069-1083. doi: 10.1177/0957650919899541 [20] 凌代军, 王晖, 马昌友. 低雷诺数亚声速扩压平面叶栅试验[J]. 航空动力学报, 2013, 28(1): 171-179. LING Daijun, WANG Hui, MA Changyou. Subsonic compressor plane cascade experiment at low Reynolds number[J]. Journal of Aerospace Power, 2013, 28(1): 171-179. (in ChineseLING Daijun, WANG Hui, MA Changyou. Subsonic compressor plane cascade experiment at low Reynolds number[J]. Journal of Aerospace Power, 2013, 28(1): 171-179. (in Chinese) [21] 魏巍, 任思源, 马护生, 等. 亚声速压气机平面叶栅雷诺数影响试验[J]. 航空动力学报, 2022, 37(5): 1020-1029. WEI Wei, REN Siyuan, MA Husheng, et al. Experiment of Reynolds number effects on subsonic compressor plane cascade[J]. Journal of Aerospace Power, 2022, 37(5): 1020-1029. (in ChineseWEI Wei, REN Siyuan, MA Husheng, et al. Experiment of Reynolds number effects on subsonic compressor plane cascade[J]. Journal of Aerospace Power, 2022, 37(5): 1020-1029. (in Chinese) [22] 常哲铭, 尹红顺, 王子登, 等. 低雷诺数压气机叶型损失机理及优化研究[J]. 燃气涡轮试验与研究, 2022, 35(5): 14-20. CHANG Zheming, YIN Hongshun, WANG Zideng, et al. Loss mechanism and optimization of low Reynolds number compressor airfoil[J]. Gas Turbine Experiment and Research, 2022, 35(5): 14-20. (in ChineseCHANG Zheming, YIN Hongshun, WANG Zideng, et al. Loss mechanism and optimization of low Reynolds number compressor airfoil[J]. Gas Turbine Experiment and Research, 2022, 35(5): 14-20. (in Chinese) [23] 王宇萌. 低雷诺数下增压级内部流动机理及调控研究[D]. 北京: 华北电力大学, 2023. WANG Yumeng. Research on internal flow mechanism and control strategies of boosters at low reynolds numbers[D]. Beijing: North China Electric Power University, 2023. (in ChineseWANG Yumeng. Research on internal flow mechanism and control strategies of boosters at low reynolds numbers[D]. Beijing: North China Electric Power University, 2023. (in Chinese) [24] 杜文海, 陈珂, 彭旻扬, 等. 进口雷诺数和湍流度对压气机叶栅流动特性影响[J]. 哈尔滨工程大学学报, 2024, 45(8): 1607-1615. DU Wenhai, CHEN Ke, PENG Minyang, et al. Influence of inlet Reynolds number and turbulent intensity on the flow mechanism in compressor profiles[J]. Journal of Harbin Engineering University, 2024, 45(8): 1607-1615. (in Chinese doi: 10.11990/jheu.202210025DU Wenhai, CHEN Ke, PENG Minyang, et al. Influence of inlet Reynolds number and turbulent intensity on the flow mechanism in compressor profiles[J]. Journal of Harbin Engineering University, 2024, 45(8): 1607-1615. (in Chinese) doi: 10.11990/jheu.202210025 [25] 朱泉钢. 中东地区军用无人机的扩散、应用及其安全影响[J]. 西亚非洲, 2022(5): 109-134, 159-160. ZHU Quangang. Proliferation, application and security implication of military drones in the middle east[J]. West Asia and Africa, 2022(5): 109-134, 159-160. (in ChineseZHU Quangang. Proliferation, application and security implication of military drones in the middle east[J]. West Asia and Africa, 2022(5): 109-134, 159-160. (in Chinese) [26] SHI Lei, GUO Shuhan, YU Peng, et al. A review on leading-edge erosion morphology and performance degradation of aero-engine fan and compressor blades[J]. Energies, 2023, 16(7): 3068. doi: 10.3390/en16073068 [27] SHI L, JIANG R, HUANG C, et al. The aerodynamic performance degradation analysis of a small high bypass turbofan engine compression system with fan rotor blade leading edge erosion[J]. The International Journal of Turbo & Jet Engines, 2024, 41(2): 211-226. [28] 史磊, 杨光, 林文俊. 前缘侵蚀对风扇转子叶片气动特性的影响机理[J]. 航空学报, 2019, 40(10): 123007. SHI Lei, YANG Guang, LIN Wenjun. Influence mechanism of leading-edge erosion on aerodynamic performance of fan rotor blade[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(10): 123007. (in ChineseSHI Lei, YANG Guang, LIN Wenjun. Influence mechanism of leading-edge erosion on aerodynamic performance of fan rotor blade[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(10): 123007. (in Chinese) [29] 史磊, 郭姝含, 马鹏宇, 等. 风扇超音叶型侵蚀前缘多目标优化修型[J]. 航空动力学报, 2025, 40(6): 20220939. SHI lei, GUO Shuhan, MA Pengyu, et al. Multi-objective optimization remodeling of eroded leading edge of supersonic fan blade[J]. Journal of Aerospace Power, 2025, 40(6): 20220939. (in ChineseSHI lei, GUO Shuhan, MA Pengyu, et al. Multi-objective optimization remodeling of eroded leading edge of supersonic fan blade[J]. Journal of Aerospace Power, 2025, 40（6）: 20220939. (in Chinese) [30] 李友淮. 低雷诺数条件下风扇流场流动的数值研究[D]. 哈尔滨: 哈尔滨工业大学, 2010. LI Youhuai. Numerical study on flow field of fan at low Reynolds number[D]. Harbin: Harbin Institute of Technology, 2010. (in ChineseLI Youhuai. Numerical study on flow field of fan at low Reynolds number[D]. Harbin: Harbin Institute of Technology, 2010. (in Chinese) [31] 顾明皓, 桂幸民. 低雷诺数效应对某型风扇的性能影响及改进方案研究[J]. 航空动力学报, 2004, 19(4): 438-443. GU Minghao, GUI Xingmin. Low-Re number effects on the performance of some fans and the modified design[J]. Journal of Aerospace Power, 2004, 19(4): 438-443. (in Chinese doi: 10.3969/j.issn.1000-8055.2004.04.002GU Minghao, GUI Xingmin. Low-Re number effects on the performance of some fans and the modified design[J]. Journal of Aerospace Power, 2004, 19(4): 438-443. (in Chinese) doi: 10.3969/j.issn.1000-8055.2004.04.002 [32] 王名扬, 赵胜丰, 李紫良, 等. 低雷诺数下高亚声速压气机叶型流动损失机理研究[J]. 推进技术, 2020, 41(5): 1046-1054. WANG Mingyang, ZHAO Shengfeng, LI Ziliang, et al. Flow and loss mechanism of high subsonic compressor airfoil under low Reynolds number conditions[J]. Journal of Propulsion Technology, 2020, 41(5): 1046-1054. (in ChineseWANG Mingyang, ZHAO Shengfeng, LI Ziliang, et al. Flow and loss mechanism of high subsonic compressor airfoil under low Reynolds number conditions[J]. Journal of Propulsion Technology, 2020, 41(5): 1046-1054. (in Chinese) [33] 尹志文, 黄嘉华. 高空长航时无人机动力装置的现状与发展[C]//第6届中国国际无人驾驶航空器系统大会论文集. 北京: 中国航空学会, 2016: 40-43. YIN Zhiwen, HUANG Jiahua. High altitude long endurance unmanned aerial vehicle status quo and development of the power plant[C]// Proceedings of the 6th China International UAS Conference. Beijing: Chinese Society of Aeronautics and Astronautics, 2016: 40-43. (in ChineseYIN Zhiwen, HUANG Jiahua. High altitude long endurance unmanned aerial vehicle status quo and development of the power plant[C]// Proceedings of the 6th China International UAS Conference. Beijing: Chinese Society of Aeronautics and Astronautics, 2016: 40-43. (in Chinese) [34] 乔渭阳, 赵磊, 罗华玲, 等. 低雷诺数涡轮叶片边界层转捩及分离特性测量[J]. 推进技术, 2012, 33(6): 859-865. QIAO Weiyang, ZHAO Lei, LUO Hualing, et al. Measurement of the transition and separation for turbine blade boundary layer with low-Reynolds number[J]. Journal of Propulsion Technology, 2012, 33(6): 859-865. (in ChineseQIAO Weiyang, ZHAO Lei, LUO Hualing, et al. Measurement of the transition and separation for turbine blade boundary layer with low-Reynolds number[J]. Journal of Propulsion Technology, 2012, 33(6): 859-865. (in Chinese) [35] POPE S B. Turbulent flow[M]. Cambridge, UK: Cambridge University Press, 2000. -
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